DUGiDocsA Micromechanics-Based Damage Model for [± θ / 90n ]s Composite Laminates
dc.contributor.author
dc.date.accessioned
2013-06-06T10:14:16Z
dc.date.available
2013-06-06T10:14:16Z
dc.date.issued
2006
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dc.description
NASA/TM-2006-214285
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A new damage model based on a micromechanical analysis of cracked [± θ / 90n ]s laminates subjected to multiaxial loads is proposed. The model predicts the onset and accumulation of transverse matrix cracks in uniformly stressed laminates, the effect of matrix cracks on the stiffness of the laminate, as well as the ultimate failure of the laminate. The model also accounts for the effect of the ply thickness on the ply strength. Predictions relating the elastic properties of several laminates and multiaxial loads are presented
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application/pdf
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eng
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National Aeronautics and Space Administration
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© NASA TM Technical Reports, 2006, núm. 214285
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Articles publicats (D-EMCI)
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Tots els drets reservats
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dc.title
A Micromechanics-Based Damage Model for [± θ / 90n ]s Composite Laminates
dc.type
info:eu-repo/semantics/article
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info:eu-repo/semantics/openAccess
dc.embargo.terms
Cap
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info:eu-repo/semantics/publishedVersion